GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 200,000 Max Cl/Cd: 79.12 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe397-il-200000-n5.txt Download as CSV file: xf-goe397-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 397 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3829 0.09684 0.09340 -0.0237 1.0000 0.0169
-7.750 -0.3799 0.09354 0.09014 -0.0245 1.0000 0.0169
-7.500 -0.3767 0.08883 0.08546 -0.0233 1.0000 0.0164
-7.250 -0.3722 0.08515 0.08178 -0.0224 1.0000 0.0156
-7.000 -0.3679 0.08199 0.07866 -0.0236 1.0000 0.0151
-6.750 -0.3625 0.07882 0.07553 -0.0253 1.0000 0.0148
-6.500 -0.3557 0.07552 0.07226 -0.0273 1.0000 0.0148
-6.250 -0.3454 0.07189 0.06865 -0.0309 1.0000 0.0158
-6.000 -0.3378 0.06869 0.06548 -0.0322 1.0000 0.0155
-5.750 -0.3078 0.06312 0.05983 -0.0406 0.9939 0.0161
-5.500 -0.2741 0.05744 0.05405 -0.0483 0.9852 0.0161
-5.250 -0.2375 0.05155 0.04800 -0.0558 0.9765 0.0162
-5.000 -0.1981 0.04485 0.04108 -0.0634 0.9668 0.0172
-4.750 -0.1745 0.04425 0.04048 -0.0647 0.9572 0.0193
-4.500 -0.1398 0.04038 0.03640 -0.0691 0.9474 0.0209
-4.250 -0.1027 0.03568 0.03140 -0.0734 0.9379 0.0220
-4.000 -0.0656 0.03099 0.02630 -0.0766 0.9271 0.0253
-3.750 -0.0305 0.02616 0.02084 -0.0783 0.9159 0.0275
-3.500 -0.0032 0.02426 0.01878 -0.0797 0.9041 0.0299
-3.250 0.0262 0.02286 0.01714 -0.0805 0.8925 0.0336
-3.000 0.0558 0.02038 0.01417 -0.0807 0.8814 0.0349
-2.750 0.0847 0.01896 0.01232 -0.0806 0.8704 0.0375
-2.500 0.1123 0.01765 0.01063 -0.0804 0.8593 0.0381
-2.250 0.1395 0.01648 0.00914 -0.0801 0.8486 0.0384
-2.000 0.1666 0.01570 0.00806 -0.0797 0.8381 0.0388
-1.500 0.2195 0.01356 0.00552 -0.0790 0.8183 0.0411
-1.250 0.2459 0.01305 0.00491 -0.0786 0.8088 0.0422
-1.000 0.2723 0.01274 0.00453 -0.0782 0.7993 0.0450
-0.750 0.2983 0.01237 0.00409 -0.0777 0.7874 0.0459
-0.500 0.3240 0.01200 0.00364 -0.0771 0.7738 0.0456
-0.250 0.3495 0.01170 0.00326 -0.0764 0.7595 0.0453
0.000 0.3752 0.01145 0.00296 -0.0758 0.7469 0.0452
0.250 0.4013 0.01125 0.00273 -0.0754 0.7365 0.0452
0.500 0.4275 0.01111 0.00254 -0.0749 0.7273 0.0454
0.750 0.4539 0.01100 0.00239 -0.0745 0.7178 0.0458
1.000 0.4803 0.01094 0.00229 -0.0741 0.7088 0.0466
1.500 0.5332 0.01087 0.00218 -0.0733 0.6912 0.0503
1.750 0.5595 0.01083 0.00218 -0.0729 0.6829 0.0611
2.000 0.6041 0.00893 0.00233 -0.0770 0.6743 1.0000
2.250 0.6301 0.00905 0.00242 -0.0766 0.6654 1.0000
2.500 0.6561 0.00918 0.00251 -0.0761 0.6569 1.0000
2.750 0.6820 0.00931 0.00264 -0.0756 0.6465 1.0000
3.000 0.7072 0.00947 0.00275 -0.0749 0.6313 1.0000
3.250 0.7321 0.00963 0.00289 -0.0742 0.6131 1.0000
3.500 0.7569 0.00979 0.00305 -0.0734 0.5926 1.0000
3.750 0.7814 0.00996 0.00320 -0.0726 0.5676 1.0000
4.000 0.8046 0.01017 0.00332 -0.0716 0.5201 1.0000
4.250 0.8257 0.01059 0.00348 -0.0702 0.4527 1.0000
4.500 0.8466 0.01115 0.00379 -0.0690 0.3983 1.0000
4.750 0.8678 0.01176 0.00421 -0.0678 0.3460 1.0000
5.000 0.8875 0.01255 0.00471 -0.0666 0.2682 1.0000
5.500 0.9196 0.01528 0.00638 -0.0636 0.0720 1.0000
5.750 0.9413 0.01593 0.00702 -0.0627 0.0564 1.0000
6.000 0.9631 0.01655 0.00769 -0.0618 0.0441 1.0000
6.250 0.9838 0.01732 0.00842 -0.0607 0.0306 1.0000
6.500 1.0042 0.01813 0.00931 -0.0595 0.0223 1.0000
6.750 1.0233 0.01907 0.01035 -0.0581 0.0184 1.0000
7.000 1.0417 0.02012 0.01154 -0.0566 0.0163 1.0000
7.250 1.0592 0.02129 0.01284 -0.0550 0.0147 1.0000
7.500 1.0760 0.02258 0.01424 -0.0534 0.0130 1.0000
7.750 1.0882 0.02500 0.01680 -0.0511 0.0112 1.0000
8.000 1.1068 0.02656 0.01856 -0.0497 0.0107 1.0000
8.250 1.1252 0.02848 0.02077 -0.0482 0.0103 1.0000
8.500 1.1431 0.03075 0.02332 -0.0468 0.0099 1.0000
8.750 1.1593 0.03337 0.02628 -0.0452 0.0095 1.0000
9.000 1.1737 0.03571 0.02893 -0.0435 0.0090 1.0000
9.250 1.1861 0.03790 0.03139 -0.0418 0.0085 1.0000
9.500 1.1973 0.03924 0.03287 -0.0402 0.0078 1.0000
9.750 1.2042 0.04130 0.03511 -0.0383 0.0074 1.0000
10.000 1.2043 0.04460 0.03874 -0.0358 0.0072 1.0000
10.250 1.1985 0.04801 0.04247 -0.0327 0.0072 1.0000
10.500 1.1871 0.05135 0.04610 -0.0294 0.0071 1.0000
11.000 1.0756 0.04958 0.04507 -0.0199 0.0073 1.0000
11.250 1.0554 0.05484 0.05056 -0.0196 0.0073 1.0000
11.500 1.0338 0.06080 0.05674 -0.0202 0.0074 1.0000
11.750 1.0106 0.06750 0.06365 -0.0218 0.0074 1.0000
12.000 0.9842 0.07527 0.07163 -0.0244 0.0075 1.0000
12.250 0.9543 0.08429 0.08087 -0.0284 0.0077 1.0000
12.500 0.9210 0.09484 0.09161 -0.0341 0.0079 1.0000
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Polar data table (+)
Polar graphs
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